US20040115040A1 - Torque tube bearing assembly - Google Patents
Torque tube bearing assembly Download PDFInfo
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- US20040115040A1 US20040115040A1 US10/316,778 US31677802A US2004115040A1 US 20040115040 A1 US20040115040 A1 US 20040115040A1 US 31677802 A US31677802 A US 31677802A US 2004115040 A1 US2004115040 A1 US 2004115040A1
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- United States
- Prior art keywords
- torque tube
- housing
- interior surface
- flange
- fan duct
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C23/00—Bearings for exclusively rotary movement adjustable for aligning or positioning
- F16C23/02—Sliding-contact bearings
- F16C23/04—Sliding-contact bearings self-adjusting
- F16C23/043—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings
- F16C23/045—Sliding-contact bearings self-adjusting with spherical surfaces, e.g. spherical plain bearings for radial load mainly, e.g. radial spherical plain bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
- F16C35/02—Rigid support of bearing units; Housings, e.g. caps, covers in the case of sliding-contact bearings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
Definitions
- the present invention relates generally to a gas turbine engine variable stator vane torque tube assembly and, more particularly, to a torque tube assembly having improved bearing life.
- Variable pitch stator vanes are commonly used in compressors of gas turbine engines.
- the variable pitch stator vanes or, more simply, variable stator vanes are pivotably mounted in axially spaced rows inside a compressor case of the engine.
- Each of the vanes pivots on a spindle having an axis extending radially with respect to an engine centerline to vary the pitch of the vane.
- Levers on the outboard ends of the spindles simultaneously pivot each of the vanes in a row.
- the levers form part of a bell crank mechanism mounted outside the compressor case.
- Some engines include a torque tube assembly operatively connecting the bell crank mechanism to a variable stator vane actuator mounted outside a fan duct surrounding the compressor case.
- the torque tube assembly includes an elongate torque tube extending through an access hole in the fan duct from the bell crank mechanism to the actuator.
- the elongate torque tube rotates in the access hole about a longitudinal axis of the tube extending generally radially relative to the engine centerline from the bell crank mechanism to the actuator. Because the compressor case and the fan duct operate at significantly different temperatures, the relative axial positions of the compressor case and the fan duct change during engine operation. As a result, the outboard end of the torque tube tilts rearward as the engine heats up during engine operation. Thus, the torque tube must be free to tilt and rotate in the access hole. To facilitate this motion, a spherical bearing assembly is positioned between the torque tube and the access hole.
- the bearing assembly includes a spherical bearing mounted on the torque tube and a housing adapted for receiving the bearing mounted over the access hole on the fan duct.
- FIG. 1 illustrates a cross section of a bearing assembly used in one such conventional variable stator vane torque tube assembly.
- This bearing assembly includes a housing tilted at an angle of less than about four degrees.
- torque tubes tilt rearward by as much as thirteen degrees or more during steady state engine operation.
- the resulting asymmetric loading developed in the bearing assembly during engine operation when the torque tube is disposed at an angle with respect to the housing has sometimes resulted in premature bearing assembly failure. Accordingly, there is a need for a torque tube assembly with a bearing that performs more reliably and has improved life under such operating conditions.
- the present invention includes a bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct of the engine.
- the torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct.
- the bearing assembly comprises a bearing adapted for mounting on the torque tube having a spherical external engagement surface.
- the assembly comprises a housing having a flange adapted for mounting on the fan duct adjacent the access hole and an annular interior surface having an inner edge and an outer edge.
- the interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between the inner edge and the outer edge of the interior surface.
- the contact plane is tilted with respect to the flange at an angle greater than five degrees.
- the invention includes a torque tube assembly for use in a gas turbine engine to connect a variable stator vane bell crank positioned inside a fan duct of the engine to a variable stator vane actuator positioned outside the fan duct.
- the torque tube assembly comprises an elongate torque tube having an inner end adapted for connection to the variable stator vane bell crank, an outer end adapted for connection to the variable stator vane actuator, and a longitudinal axis extending between the inner end and the outer end.
- the assembly comprises a bearing mounted on the torque tube having a spherical external engagement surface and a housing having a flange adapted for mounting to the fan duct and an annular interior surface having an inner edge and an outer edge.
- the interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so that when the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane extending parallel to the outer edge of the interior surface of the housing, the torque tube axis extends at an angle of less than 85° from the flange.
- FIG. 1 is a cross section of a prior art bearing assembly
- FIG. 2 is a section of a portion of a gas turbine engine showing a torque tube bearing assembly of the present invention
- FIG. 3 is a cross section of a bearing assembly of the present invention.
- FIG. 4 is a top plan of the bearing assembly of the present invention.
- a torque tube assembly for use in a gas turbine engine is designated in its entirety by the reference numeral 20 .
- the assembly 20 extends through an access hole 24 in a fan duct 26 of the gas turbine engine (generally designated by 28 ) and connects a variable stator vane bell crank (generally designated by 30 ) positioned inside the fan duct to an actuator (generally designated by 32 ) positioned outside the fan duct.
- the torque tube assembly 20 transmits torque from the actuator 32 to the bell crank 30 to vary the pitch of stator vanes 34 connected to the bell crank.
- the vanes, generally designated by 34 are mounted inside a compressor case 36 of the engine 28 .
- the vanes 34 direct air passing through a flowpath 38 of the engine 28 inside the compressor case 36 .
- Each of the vanes 34 includes a spindle 40 extending through a bushing 42 mounted on the compressor case 36 .
- a lever 44 forming part of the bell crank 30 is mounted on an outboard end 46 of each spindle 40 .
- the levers 44 provide leverage to pivot the vanes 34 about their respective spindles 40 to vary their pitch or angle of attack with respect to the air flowing through the flowpath 38 of the engine 28 .
- the torque tube assembly 20 comprises a conventional elongate torque tube, generally designated by 50 , having an inner end 52 adapted for connection to the variable stator vane bell crank 30 , an outer end 54 adapted for connection to the variable stator vane actuator 32 , and an imaginary longitudinal axis 56 extending between the inner and outer ends.
- a bearing generally designated by 60 , is mounted on the torque tube 50 .
- the bearing 60 has a spherical external engagement surface 62 and an internal bore 64 adapted for receiving the torque tube 50 .
- the torque tube assembly 20 also includes a housing, generally designated by 70 , having an annular interior surface 72 adapted for rotatably receiving the spherical external engagement surface 62 of the bearing 60 . As illustrated in FIG. 3, the annular interior surface 72 has an inner edge 74 and an outer edge 76 . Together the bearing 60 and housing 70 form a bearing assembly, generally designated by 80 , for mounting the torque tube 50 in the access hole 24 of the fan duct 26 .
- the bearing assembly 80 permits the torque tube 50 to rotate about its longitudinal axis 56 to pivot the vanes 34 , as well as tilt within the access hole 24 of the fan duct 26 to compensate for differences in thermal growth between the compressor case 36 and fan duct 26 during engine 28 operation.
- the housing 70 has a flange 82 adapted for mounting the housing to the fan duct 26 so the annular interior surface 72 of the housing is aligned with the access hole 24 in the fan duct.
- the flange 82 is constructed integrally with the housing 70 .
- the flange 82 includes a plurality of holes 84 for attaching the housing 70 to the fan duct 26 with bolts (not shown) or other fasteners.
- the housing 70 also has an annular rabbet surface 86 for engaging the access hole 24 when the flange 82 is mounted on the fan duct 26 to properly position the bearing assembly 80 on the fan duct.
- the annular interior surface 72 of the housing 70 includes a relieved portion 90 for loading the bearing 60 into the housing 70 .
- the relieved portion 90 faces inward when the flange 82 of the housing 70 is mounted on the fan duct 26 so the bearing 60 loads outward against an uninterrupted portion 92 of the interior surface 72 of the housing.
- the spherical external engagement surface 62 of the bearing 60 and the annular interior surface 72 of the housing 70 make contact along an annular contact area (the outer and inner boundaries of which are designated by dashed lines 100 ) centered on a contact plane 102 lying between the inner edge 74 and the outer edge 76 of the interior surface 72 .
- the contact plane 102 is tilted with respect to the flange 82 at an angle 104 greater than five degrees. This arrangement results in the torque tube axis 56 extending at an angle 106 (FIG.
- the angle 104 at which the contact plane 102 tilts is greater than about ten degrees resulting in an angle 106 of less than about eighty degrees. In another embodiment, the angle 104 at which the contact plane 102 tilts is about thirteen degrees resulting in an angle 106 of about 77 degrees. In still another embodiment, the angle 104 is about 13.08 degrees. As will be appreciated by those skilled in the art, the angle 106 is optimally the angle at which the torque tube 50 passes through the access hole 24 during a steady state power setting of the engine.
- the angle 106 is the angle at which the torque tube 50 passes through the access hole 24 during steady state cruise operation of the engine.
- the outer end 54 of the torque tube 50 is positioned behind the inner end 52 of the torque tube during the steady state power setting of the engine 28 .
- the torque tube axis 56 may be substantially radial when the engine 28 is cold to enhance engine assembly.
- the angles 104 , 106 result in the torque tube axis 56 extending perpendicular to the outside edge 76 of the interior surface 72 of the housing 70 during at least one steady state power setting of the engine 28 (e.g., during steady state cruise operation of an aircraft engine).
- This arrangement also results in a rearward side 110 of the housing flange 82 being positioned outboard from the outer edge 76 of the interior surface 72 of the housing 70 when the flange is mounted on the fan duct 26 and a forward side 112 of the housing flange being positioned inboard from at least a portion of the interior surface of the housing when the flange is mounted on the fan duct.
- Each of the previously described components of the torque tube assembly 20 may be constructed from materials conventionally used to construct torque tube assemblies.
- the housing 70 may be made of other materials without departing from the scope of the present invention, in one embodiment the housing is made from stainless steel.
- a portion of the interior surface 72 of the housing 70 e.g., the spherical portion 90 of the interior surface
- the bearing 60 may be made of other materials without departing from the scope of the present invention, in one embodiment the bearing is made from stainless steel.
- the torque tube assembly 20 operates conventionally. As the actuator 32 extends and retracts, the torque tube 50 rotates about its longitudinal axis 56 within the access hole 24 of the fan duct 26 to drive the bell crank 30 and thereby vary the pitch of the stator vanes 34 inside the compressor case 36 . Further, the bearing assembly 80 permits the torque tube to tilt to compensate for differences in thermal growth between the fan duct 26 and the compressor case 36 .
- the torque tube assembly 20 of the present invention has improved load distribution on the bearing 60 and housing 70 during engine operation. This results in improved life and improved performance of the bearing assembly 80 consequently improving the life and performance of torque tube assembly 20 and the gas turbine engine.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Sliding-Contact Bearings (AREA)
- Mounting Of Bearings Or Others (AREA)
- Support Of The Bearing (AREA)
Abstract
Description
- [0001] This invention was made with government support under grants from the U.S. Department of Defense (F33657-99-D-2050 EPD Z123D12). The U.S. government has certain rights in this invention.
- The present invention relates generally to a gas turbine engine variable stator vane torque tube assembly and, more particularly, to a torque tube assembly having improved bearing life.
- Variable pitch stator vanes are commonly used in compressors of gas turbine engines. The variable pitch stator vanes or, more simply, variable stator vanes are pivotably mounted in axially spaced rows inside a compressor case of the engine. Each of the vanes pivots on a spindle having an axis extending radially with respect to an engine centerline to vary the pitch of the vane. Levers on the outboard ends of the spindles simultaneously pivot each of the vanes in a row. The levers form part of a bell crank mechanism mounted outside the compressor case. Some engines include a torque tube assembly operatively connecting the bell crank mechanism to a variable stator vane actuator mounted outside a fan duct surrounding the compressor case. The torque tube assembly includes an elongate torque tube extending through an access hole in the fan duct from the bell crank mechanism to the actuator.
- During operation, the elongate torque tube rotates in the access hole about a longitudinal axis of the tube extending generally radially relative to the engine centerline from the bell crank mechanism to the actuator. Because the compressor case and the fan duct operate at significantly different temperatures, the relative axial positions of the compressor case and the fan duct change during engine operation. As a result, the outboard end of the torque tube tilts rearward as the engine heats up during engine operation. Thus, the torque tube must be free to tilt and rotate in the access hole. To facilitate this motion, a spherical bearing assembly is positioned between the torque tube and the access hole. The bearing assembly includes a spherical bearing mounted on the torque tube and a housing adapted for receiving the bearing mounted over the access hole on the fan duct.
- Some conventional variable stator vane torque tube assemblies have housings tilted to match the calculated torque tube tilt angle during engine operation. FIG. 1 illustrates a cross section of a bearing assembly used in one such conventional variable stator vane torque tube assembly. This bearing assembly includes a housing tilted at an angle of less than about four degrees. However, in some instances torque tubes tilt rearward by as much as thirteen degrees or more during steady state engine operation. The resulting asymmetric loading developed in the bearing assembly during engine operation when the torque tube is disposed at an angle with respect to the housing has sometimes resulted in premature bearing assembly failure. Accordingly, there is a need for a torque tube assembly with a bearing that performs more reliably and has improved life under such operating conditions.
- Briefly, the present invention includes a bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct of the engine. The torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct. The bearing assembly comprises a bearing adapted for mounting on the torque tube having a spherical external engagement surface. Further, the assembly comprises a housing having a flange adapted for mounting on the fan duct adjacent the access hole and an annular interior surface having an inner edge and an outer edge. The interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between the inner edge and the outer edge of the interior surface. The contact plane is tilted with respect to the flange at an angle greater than five degrees.
- In another aspect, the invention includes a torque tube assembly for use in a gas turbine engine to connect a variable stator vane bell crank positioned inside a fan duct of the engine to a variable stator vane actuator positioned outside the fan duct. The torque tube assembly comprises an elongate torque tube having an inner end adapted for connection to the variable stator vane bell crank, an outer end adapted for connection to the variable stator vane actuator, and a longitudinal axis extending between the inner end and the outer end. Further, the assembly comprises a bearing mounted on the torque tube having a spherical external engagement surface and a housing having a flange adapted for mounting to the fan duct and an annular interior surface having an inner edge and an outer edge. The interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so that when the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane extending parallel to the outer edge of the interior surface of the housing, the torque tube axis extends at an angle of less than 85° from the flange.
- Other features of the present invention will be in part apparent and in part pointed out hereinafter.
- FIG. 1 is a cross section of a prior art bearing assembly;
- FIG. 2 is a section of a portion of a gas turbine engine showing a torque tube bearing assembly of the present invention;
- FIG. 3 is a cross section of a bearing assembly of the present invention; and
- FIG. 4 is a top plan of the bearing assembly of the present invention.
- Corresponding reference characters indicate corresponding parts throughout the several views of the drawings.
- Referring now to the drawings and in particular to FIG. 2, a torque tube assembly for use in a gas turbine engine is designated in its entirety by the
reference numeral 20. Theassembly 20 extends through anaccess hole 24 in afan duct 26 of the gas turbine engine (generally designated by 28) and connects a variable stator vane bell crank (generally designated by 30) positioned inside the fan duct to an actuator (generally designated by 32) positioned outside the fan duct. Thetorque tube assembly 20 transmits torque from theactuator 32 to thebell crank 30 to vary the pitch ofstator vanes 34 connected to the bell crank. The vanes, generally designated by 34, are mounted inside acompressor case 36 of theengine 28. Thevanes 34 direct air passing through aflowpath 38 of theengine 28 inside thecompressor case 36. Each of thevanes 34 includes aspindle 40 extending through abushing 42 mounted on thecompressor case 36. Alever 44 forming part of thebell crank 30 is mounted on anoutboard end 46 of eachspindle 40. Thelevers 44 provide leverage to pivot thevanes 34 about theirrespective spindles 40 to vary their pitch or angle of attack with respect to the air flowing through theflowpath 38 of theengine 28. - As further illustrated in FIG. 2, the
torque tube assembly 20 comprises a conventional elongate torque tube, generally designated by 50, having aninner end 52 adapted for connection to the variable statorvane bell crank 30, anouter end 54 adapted for connection to the variablestator vane actuator 32, and an imaginarylongitudinal axis 56 extending between the inner and outer ends. The features of the torque tube are conventional and will not be discussed in detail. A bearing, generally designated by 60, is mounted on thetorque tube 50. Thebearing 60 has a sphericalexternal engagement surface 62 and aninternal bore 64 adapted for receiving thetorque tube 50. Although thebearing 60 may be mounted on thetorque tube 50 in other ways without departing from the scope of the present invention, in one embodiment theinternal bore 64 is sized for a close clearance fit with the torque tube so the bearing and torque tube move as a unit. Thetorque tube assembly 20 also includes a housing, generally designated by 70, having an annularinterior surface 72 adapted for rotatably receiving the sphericalexternal engagement surface 62 of thebearing 60. As illustrated in FIG. 3, the annularinterior surface 72 has aninner edge 74 and anouter edge 76. Together the bearing 60 andhousing 70 form a bearing assembly, generally designated by 80, for mounting thetorque tube 50 in theaccess hole 24 of thefan duct 26. Thebearing assembly 80 permits thetorque tube 50 to rotate about itslongitudinal axis 56 to pivot thevanes 34, as well as tilt within theaccess hole 24 of thefan duct 26 to compensate for differences in thermal growth between thecompressor case 36 andfan duct 26 duringengine 28 operation. - As illustrated in FIG. 3, the
housing 70 has aflange 82 adapted for mounting the housing to thefan duct 26 so the annularinterior surface 72 of the housing is aligned with theaccess hole 24 in the fan duct. In one embodiment, theflange 82 is constructed integrally with thehousing 70. As illustrated in FIG. 4, theflange 82 includes a plurality ofholes 84 for attaching thehousing 70 to thefan duct 26 with bolts (not shown) or other fasteners. As shown in FIG. 3, thehousing 70 also has anannular rabbet surface 86 for engaging theaccess hole 24 when theflange 82 is mounted on thefan duct 26 to properly position thebearing assembly 80 on the fan duct. In one embodiment, the annularinterior surface 72 of thehousing 70 includes a relievedportion 90 for loading thebearing 60 into thehousing 70. The relievedportion 90 faces inward when theflange 82 of thehousing 70 is mounted on thefan duct 26 so the bearing 60 loads outward against anuninterrupted portion 92 of theinterior surface 72 of the housing. - As will be appreciated by those skilled in the art, the spherical
external engagement surface 62 of thebearing 60 and the annularinterior surface 72 of thehousing 70 make contact along an annular contact area (the outer and inner boundaries of which are designated by dashed lines 100) centered on acontact plane 102 lying between theinner edge 74 and theouter edge 76 of theinterior surface 72. Thecontact plane 102 is tilted with respect to theflange 82 at anangle 104 greater than five degrees. This arrangement results in thetorque tube axis 56 extending at an angle 106 (FIG. 2) measured from the flange of less than 85 degrees when thetube 50 is tilted so the tube is centered with respect to the inner andouter edges interior surface 72 of thehousing 70. In one embodiment, theangle 104 at which thecontact plane 102 tilts is greater than about ten degrees resulting in anangle 106 of less than about eighty degrees. In another embodiment, theangle 104 at which thecontact plane 102 tilts is about thirteen degrees resulting in anangle 106 of about 77 degrees. In still another embodiment, theangle 104 is about 13.08 degrees. As will be appreciated by those skilled in the art, theangle 106 is optimally the angle at which thetorque tube 50 passes through theaccess hole 24 during a steady state power setting of the engine. For example, if theengine 28 is an aircraft engine, theangle 106 is the angle at which thetorque tube 50 passes through theaccess hole 24 during steady state cruise operation of the engine. Further, in one embodiment theouter end 54 of thetorque tube 50 is positioned behind theinner end 52 of the torque tube during the steady state power setting of theengine 28. In addition, thetorque tube axis 56 may be substantially radial when theengine 28 is cold to enhance engine assembly. Those skilled in the art will appreciate theangles torque tube axis 56 extending perpendicular to theoutside edge 76 of theinterior surface 72 of thehousing 70 during at least one steady state power setting of the engine 28 (e.g., during steady state cruise operation of an aircraft engine). This arrangement also results in arearward side 110 of thehousing flange 82 being positioned outboard from theouter edge 76 of theinterior surface 72 of thehousing 70 when the flange is mounted on thefan duct 26 and aforward side 112 of the housing flange being positioned inboard from at least a portion of the interior surface of the housing when the flange is mounted on the fan duct. - Each of the previously described components of the
torque tube assembly 20 may be constructed from materials conventionally used to construct torque tube assemblies. Although thehousing 70 may be made of other materials without departing from the scope of the present invention, in one embodiment the housing is made from stainless steel. A portion of theinterior surface 72 of the housing 70 (e.g., thespherical portion 90 of the interior surface) may be coated with a protective coating and/or a friction reducing coating to reduce wear. Although thebearing 60 may be made of other materials without departing from the scope of the present invention, in one embodiment the bearing is made from stainless steel. - As will be appreciated by those skilled in the art, the
torque tube assembly 20 operates conventionally. As theactuator 32 extends and retracts, thetorque tube 50 rotates about itslongitudinal axis 56 within theaccess hole 24 of thefan duct 26 to drive the bell crank 30 and thereby vary the pitch of thestator vanes 34 inside thecompressor case 36. Further, the bearingassembly 80 permits the torque tube to tilt to compensate for differences in thermal growth between thefan duct 26 and thecompressor case 36. Thetorque tube assembly 20 of the present invention has improved load distribution on thebearing 60 andhousing 70 during engine operation. This results in improved life and improved performance of the bearingassembly 80 consequently improving the life and performance oftorque tube assembly 20 and the gas turbine engine. - When introducing elements of the present invention or the preferred embodiment(s) thereof, the articles “a”, “an”, “the” and “said” are intended to mean that there are one or more of the elements. The terms “comprising”, “including” and “having” are intended to be inclusive and mean that there may be additional elements other than the listed elements.
- As various changes could be made in the above constructions without departing from the scope of the invention, it is intended that all matter contained in the above description or shown in the accompanying drawings shall be interpreted as illustrative and not in a limiting sense.
Claims (19)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
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US10/316,778 US6821084B2 (en) | 2002-12-11 | 2002-12-11 | Torque tube bearing assembly |
SG200305923A SG121807A1 (en) | 2002-12-11 | 2003-10-08 | Torque tube bearing assembly |
DE60312293T DE60312293T2 (en) | 2002-12-11 | 2003-10-09 | Bearing arrangement for a torsion tube |
EP03256367A EP1428986B1 (en) | 2002-12-11 | 2003-10-09 | Torque tube bearing assembly |
KR1020030070514A KR100814169B1 (en) | 2002-12-11 | 2003-10-10 | Torque tube bearing assembly |
JP2003351742A JP4398694B2 (en) | 2002-12-11 | 2003-10-10 | Torque tube bearing assembly |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/316,778 US6821084B2 (en) | 2002-12-11 | 2002-12-11 | Torque tube bearing assembly |
Publications (2)
Publication Number | Publication Date |
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US20040115040A1 true US20040115040A1 (en) | 2004-06-17 |
US6821084B2 US6821084B2 (en) | 2004-11-23 |
Family
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US10/316,778 Expired - Fee Related US6821084B2 (en) | 2002-12-11 | 2002-12-11 | Torque tube bearing assembly |
Country Status (6)
Country | Link |
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US (1) | US6821084B2 (en) |
EP (1) | EP1428986B1 (en) |
JP (1) | JP4398694B2 (en) |
KR (1) | KR100814169B1 (en) |
DE (1) | DE60312293T2 (en) |
SG (1) | SG121807A1 (en) |
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US20160003293A1 (en) * | 2014-07-01 | 2016-01-07 | SKF Aerospace France S.A.S | Spherical plain bearing with inner sleeve |
US9429169B2 (en) | 2009-11-20 | 2016-08-30 | Snecma | Turbine engine having a stage of variable-pitch stator vanes with independent control |
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US7360990B2 (en) * | 2004-10-13 | 2008-04-22 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
US8015996B2 (en) * | 2005-04-28 | 2011-09-13 | United Technologies Corporation | Gas turbine engine air valve assembly |
US8435000B2 (en) * | 2008-03-07 | 2013-05-07 | Rolls-Royce Corporation | Variable vane actuation system |
US8393857B2 (en) * | 2009-10-09 | 2013-03-12 | Rolls-Royce Corporation | Variable vane actuation system |
US8360716B2 (en) * | 2010-03-23 | 2013-01-29 | United Technologies Corporation | Nozzle segment with reduced weight flange |
US9039355B2 (en) | 2012-05-31 | 2015-05-26 | United Technologies Corporation | Actuator mounted to torque box |
US9151178B2 (en) * | 2012-11-15 | 2015-10-06 | United Technologies Corporation | Bellcrank for a variable vane assembly |
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RU2578783C1 (en) * | 2015-03-19 | 2016-03-27 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" | Unit for connection of power cylinder drive of guide vanes with gas turbine engine intermediate housing |
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- 2002-12-11 US US10/316,778 patent/US6821084B2/en not_active Expired - Fee Related
-
2003
- 2003-10-08 SG SG200305923A patent/SG121807A1/en unknown
- 2003-10-09 EP EP03256367A patent/EP1428986B1/en not_active Expired - Fee Related
- 2003-10-09 DE DE60312293T patent/DE60312293T2/en not_active Expired - Lifetime
- 2003-10-10 KR KR1020030070514A patent/KR100814169B1/en not_active IP Right Cessation
- 2003-10-10 JP JP2003351742A patent/JP4398694B2/en not_active Expired - Fee Related
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US9429169B2 (en) | 2009-11-20 | 2016-08-30 | Snecma | Turbine engine having a stage of variable-pitch stator vanes with independent control |
US20160003293A1 (en) * | 2014-07-01 | 2016-01-07 | SKF Aerospace France S.A.S | Spherical plain bearing with inner sleeve |
US9695869B2 (en) * | 2014-07-01 | 2017-07-04 | SKF Aerospace France S.A.S | Spherical plain bearing with inner sleeve |
Also Published As
Publication number | Publication date |
---|---|
EP1428986A2 (en) | 2004-06-16 |
KR20040051489A (en) | 2004-06-18 |
KR100814169B1 (en) | 2008-03-14 |
JP4398694B2 (en) | 2010-01-13 |
SG121807A1 (en) | 2006-05-26 |
DE60312293T2 (en) | 2007-11-08 |
US6821084B2 (en) | 2004-11-23 |
DE60312293D1 (en) | 2007-04-19 |
EP1428986B1 (en) | 2007-03-07 |
JP2004190660A (en) | 2004-07-08 |
EP1428986A3 (en) | 2005-06-15 |
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